Hydrogen supply system for an aircraft engine with a turbo-pump and a low-pressure burner

A hydrogen supply system for supplying gaseous hydrogen to a turbine engine of an aircraft, the hydrogen supply system comprising:

• a first pump configured to receive liquid hydrogen from a liquid hydrogen tank of the aircraft and produce a pressurized liquid hydrogen;
• a second pump configured to receive the pressurized liquid hydrogen from the first pump and produce a highly pressurized liquid hydrogen;
• a heat exchanger configured to receive, at a first input port, the highly pressurized liquid hydrogen from the second pump and provide, at a first output port, a gaseous heated pressurized hydrogen;
• a turbine configured to receive, at an input port, the gaseous heated pressurized hydrogen from the first output port of the heat exchanger and to provide, at an output port, gaseous hydrogen, wherein the turbine provides mechanical energy to the second pump to operate the second pump;
• an output pipe having a first end fluidly connected to the output port of the turbine and to the first output port of the heat exchanger and a second end intended to be fluidly connected to the turbine engine;
• a combustion chamber comprising a first input port configured to receive air at a pressure close to ambient, a second input port fluidly connected to the output port of the turbine and to the first output port of the heat exchanger, and an output port fluidly connected to a second input port of the heat exchanger;
• a first valve configured to control the quantity of gaseous heated pressurized hydrogen entering in the input port of the turbine;
• a second valve configured to control the quantity of gaseous heated pressurized hydrogen entering in the second input port of the combustion chamber;
• and
• a control unit configured to control an opening and a closing of each valve.